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爆轰双向驱动双状态并行技术的原理性研究

中国科学：技术科学 2024年第3期54卷 530-544页

作者：杨帆林明月胡宗民韩桂来中国科学院力学研究所高温气体动力学国家重点实验室北京100190 中国科学院大学工程科学学院北京100049

爆轰驱动激波风洞是用来产生高超声速高焓试验气流的地面试验装置,通常分为正向爆轰驱动激波风洞和反向爆轰驱动激波风洞两种.本文针对单独正向或反向驱动模式的不足,提出一种新型的爆轰双向驱动模式,同时利用爆轰波的高能波阵面和泰勒... 详细信息

爆轰驱动激波风洞是用来产生高超声速高焓试验气流的地面试验装置,通常分为正向爆轰驱动激波风洞和反向爆轰驱动激波风洞两种.本文针对单独正向或反向驱动模式的不足,提出一种新型的爆轰双向驱动模式,同时利用爆轰波的高能波阵面和泰勒稀疏波尾部平稳端,在一次试验中同时实现中焓与高焓两种高超声速试验气流.本文利用高温热化学反应流动数值计算技术,模拟并分析了爆轰双向驱动激波风洞中的关键波动力学过程,数值计算结果表明,爆轰双向驱动技术是可行的,而且正向驱动端和反向驱动端的状态调整具有相对独立性,可以覆盖中高焓大范围跨流域试验能力.

关键词：高焓试验气流爆轰双向驱动激波风洞热化学反应流动缝合界面条件

Advances in critical technologies for hypersonic and high-enthalpy wind tunnel

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Chinese Journal of Aeronautics 2020年第12期33卷 3027-3038页

作者： Zonglin JIANG Zongmin HU Yunpeng WANG guilai han State Key Laboratory of High-temperature Gas Dynamics(LHD) Institute of MechanicsChinese Academy of SciencesBeijing 100190China School of Engineering Science University of Chinese Academy of SciencesBeijing 100049China

Hypersonic and high-enthalpy wind tunnels and their measurement techniques are the cornerstone of the hypersonic flight era that is a dream for human beings to fly faster,higher and further.The great progress has been achieved during the recent years and their critical technologies are still in an urgent need for further development.There are at least four kinds of hypersonic and high-enthalpy wind tunnels that are widely applied over the world and can be classified according to their operation modes.These wind tunnels are named as air-directly-heated hypersonic wind tunnel,light-gas-heated shock tunnel,free-piston-driven shock tunnel and detonation-driven shock tunnel,respectively.The critical technologies for developing the wind tunnels are introduced in this paper,and their merits and weakness are discussed based on wind tunnel performance evaluation.Measurement techniques especially developed for high-enthalpy flows are a part of the hypersonic wind tunnel technology because the flow is a chemically reacting gas motion and its diagnosis needs specially designed instruments.Three kinds of the measurement techniques considered to be of primary importance are introduced here,including the heat flux sensor,the aerodynamic balance,and optical diagnosis techniques.The techniques are developed usually for conventional wind tunnels,but further improved for hypersonic and high-enthalpy tunnels.The hypersonic ground test facilities have provided us with most of valuable experimental data on high-enthalpy flows and will play a more important role in hypersonic research area in the future.Therefore,several prospects for developing hypersonic and high-enthalpy wind tunnels are presented from our point of view.

关键词： High-enthalpy flow Hypersonic wind tunnel Aerospace vehicle Aerodynamic balance Heat flux sensor Optical measurement technique

Simulation of shear layers interaction and unsteady evolution under different double backward-facing steps

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Theoretical & Applied Mechanics Letters 2020年第4期10卷 224-229页

作者： Fang Deng guilai han Zonglin Jiang State Key Laboratory of High Temperature Gas Dynamics Institute of MechanicsChinese Academy of SciencesBeijing 100049China School of Engineering Science Chinese Academy of SciencesBeijing 100049China

High-order accurate schemes are employed to numerically simulate the interaction of a supersonic jet and a co-directional supersonic inflow. A double backward-facing step model is proposed to investigate the interaction between the jet shear layer and the supersonic inflow shear layer. It is found that due to the interaction of the shear layer, a secondary jet is injected into the recirculation zone at the intersection of the two shear layers. The secondary jet produced by the interaction of the two shear layers has a periodicity because of shear layers interaction. The distinction in the shape of double backward-facing steps will induce changes in the period of the secondary jet. The analysis and discussion of the periodicity of the secondary jet are mainly focused in this letter.

关键词： Shear layer Interaction Unsteady evolution Jet Numerical simulation

Noise reduction for temperature-sensitive paint measurement contaminated by strong background radiation in a high enthalpy hypersonic tunnel

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Acta Mechanica Sinica 2021年第1期37卷 20-26,I0002页

作者： Di Peng Xu Liu Lingrui Jiao Ziyan Li Xin Wen Chaokai Yuan guilai han Yunfeng Liu Yingzheng Liu Zonglin Jiang Gas Turbine Research Institute/School of Mechanical Engineering Shanghai Jiao Tong UniversityShanghai200240China Institute of Mechanics Chinese Academy of SciencesBeijing100190China

The strong background radiation in high enthalpy hypersonic shock tunnels has posed severe challenges for measurement using luminescent coatings.We proposed a solution for reducing background radiation from time-resolved temperature-sensitive paint(TSP)measurement in a hypersonic flow with Ma=6.5 and T_(0)=3525 K.The TSP was applied on an inlet ramp model,and the images were taken by a high-speed camera at 2 kHz under a modulated excitation.The strong background radiation led to a low signal-to-noise ratio and significant errors for the first half of the 130-ms test duration.Accordingly,three noise reduction methods were developed and evaluated based on temporal reconstruction,spatial reconstruction and robust principal component analysis(RPCA),respectively.The RPCA method showed the best performance that successfully recovered high-quality TSP data for a majority of test duration(t≥40 ms).

关键词： Temperature-sensitive paint Time-resolved measurement Hypersonic flow Background radiation

Experimental demonstration of a new concept of drag reduction and thermal protection for hypersonic vehicles

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Acta Mechanica Sinica 2009年第3期25卷 417-419页

作者： Zonglin Jiang Yunfeng Liu guilai han Wei Zhao Key Laboratory of High Temperature Gas Dynamics, Institute of Mechanics, Chinese Academy of Sciences, 100190 Beijing, China Key Laboratory of High Temperature Gas Dynamics Institute of Mechanics Chinese Academy of Sciences Beijing China

A new idea of drag reduction and thermal protection for hypersonic vehicles is proposed based on the combination of a physical spike and lateral jets for shockreconstruction. The spike recasts the bow shock in front of a blunt body into a conical shock, and the lateral jets work to protect the spike tip from overheating and to push the conical shock away from the blunt body when a pitching angle exists during flight. Experiments are conducted in a hypersonic wind tunnel at a nominal Mach number of 6. It is demonstrated that the shock/shock interaction on the blunt body is avoided due to injection and the peak pressure at the reattachment point is reduced by 70% under a 4° attack angle.

关键词： Hypersonic vehicle Shock-reconstruction. Drag reduction Thermal protection Spike and lateral jets

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高超声速边界层液膜演化过程和冷却机理研究

力学学报 2023年第5期55卷 1039-1052页

作者：骆寅涛韩桂来钱丽娟姜宗林刘美宽中国计量大学机电工程学院杭州310000 中国科学院力学研究所高温气体动力学国家重点实验室北京100190 中国科学院大学工程科学学院北京100190

高超声速液膜冷却技术是通过一系列狭缝或孔洞压出冷却工质,在飞行器表面边界层形成一层低温冷却膜,阻止高超声速气流对飞行器的气动加热.其作为一种主动冷却方式在高超声速飞行器表面热防护有着巨大的应用潜力.文章采用数值方法,结合VO... 详细信息

高超声速液膜冷却技术是通过一系列狭缝或孔洞压出冷却工质,在飞行器表面边界层形成一层低温冷却膜,阻止高超声速气流对飞行器的气动加热.其作为一种主动冷却方式在高超声速飞行器表面热防护有着巨大的应用潜力.文章采用数值方法,结合VOF模型,研究25 km飞行高度和Ma=5气流条件下的液膜铺展情况,并通过不同冷却工质的入射速度、角度、表面张力和黏性系数条件,讨论了液膜在平板上的演化过程和冷却机理.结果表明,在气流作用下,液膜向壁面下游发展,液膜的存在导致边界层分离,连续液膜会在一定位置断裂为液块,然后进一步破碎为液滴.入射条件和液体性质的改变,会影响液膜沿流向的发展,具体表现在连续液膜断裂点的位置和连续液膜的厚度.在所设定的计算域内,壁面热流降低了80%~95%,液膜对壁面的冷却效率随着液膜形态的变化而变化.

关键词：高超声速液膜冷却液膜演化壁面热流 VOF

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结构振动对大型激波风洞气动力测量的干扰

力学学报 2016年第1期48卷 102-110页

作者：孟宝清韩桂来姜宗林中国科学院力学研究所高温气体动力学国家重点实验室北京100190

激波风洞起动过程形成冲击载荷激励测力系统的结构振动,气动力测量过程中振动尚未衰减,测力过程可以看作是一个动态的过程,激波风洞中天平输出信号包含了振动干扰的输出信号,现有的解决方法缺乏理论支撑,精度受限.本文应用振动理论方法... 详细信息

激波风洞起动过程形成冲击载荷激励测力系统的结构振动,气动力测量过程中振动尚未衰减,测力过程可以看作是一个动态的过程,激波风洞中天平输出信号包含了振动干扰的输出信号,现有的解决方法缺乏理论支撑,精度受限.本文应用振动理论方法,得到了自由振动、强迫振动特性的基本解析结果.自由振动特性研究中考查了单个振型对测力的干扰及其影响规律以及干扰量幅值随测力截面相对位置的变化规律.强迫振动特性研究了不同载荷强迫振动下各阶振型对测力的干扰.研究表明,由于干扰量幅值与加速度幅值的"零点位置"不重合,传统加速度惯性补偿存在理论上的缺陷.实验中确定干扰量主要来源需要综合考虑截面位置、载荷作用位置、载荷类型的影响.

关键词：激波风洞气动力测量振动干扰理论求解

JF-12激波风洞在火星进入环境下的运行特性

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航空学报 2021年第3期42卷 183-194页

作者：韩子健彭俊胡宗民韩桂来姜宗林中国科学院力学研究所高温气体动力学国家重点实验室北京100190 中国科学院大学工程科学学院北京100049

火星探测是目前国际深空探测的热点,而火星着陆是火星探测的关键技术之一,火星着陆器发展中面临的一个严峻的挑战是其气动环境远远不同于地球大气的空气。然而,现阶段大多数地面试验设备都是以空气为试验气体来设计的,而不是火星大气的... 详细信息

火星探测是目前国际深空探测的热点,而火星着陆是火星探测的关键技术之一,火星着陆器发展中面临的一个严峻的挑战是其气动环境远远不同于地球大气的空气。然而,现阶段大多数地面试验设备都是以空气为试验气体来设计的,而不是火星大气的CO2。本文利用高温热化学反应流动数值计算技术,对JF-12反向爆轰驱动激波风洞在火星进入环境下(主要气体成分是CO2)的运行特性进行了计算模拟,通过调整激波管中驱动/被驱动气体的初始参数和高/低压段的截面积比,来模拟其中的波系产生、传播过程以及反射激波与接触面的相互作用机制。研究发现,相同情况下驱动CO2的缝合激波马赫数要明显高于空气,通过减小驱动气体的声速和低压段的直径,可以在驱动CO2时获得驻室压力稳定的试验气体。

关键词：火星探测反向爆轰驱动激波风洞二氧化碳缝合运行状态驻室压力

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激波与爆轰波对撞的数值模拟研究

力学学报 2008年第2期40卷 154-161页

作者：韩桂来姜宗林张德良中国科学院力学研究所高温气体动力学重点实验室北京100080

采用二阶精度NND差分格式和改进的二阶段化学反应模型模拟了爆轰波与激波的对撞过程,研究了不同强度入射激波对爆轰过渡区域的影响.当对撞激波较弱时,透射爆轰波演变主要受流动膨胀作用的影响,可划分为对撞影响区、爆轰恢复区和稳定发展... 详细信息

采用二阶精度NND差分格式和改进的二阶段化学反应模型模拟了爆轰波与激波的对撞过程,研究了不同强度入射激波对爆轰过渡区域的影响.当对撞激波较弱时,透射爆轰波演变主要受流动膨胀作用的影响,可划分为对撞影响区、爆轰恢复区和稳定发展区3个阶段,在爆轰恢复区和稳定发展区,前导激波压力经历一个过冲、然后向稳定爆轰过渡的过程,表现了爆轰波熄爆和再起爆的物理特征,当对撞激波较强时,可燃混合气体的高热力学参数导致了更高的化学反应活化程度,形成了弱爆轰向稳定爆轰的直接转变.

关键词：激波对撞过渡区域爆轰波激波数值模拟